A.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- i 

### SECTION 5

PERFORMANCE

TABLE OF CONTENTS

P ARAGRAPH P AGE

5.1 GENERAL 5

- 1

5.2 INTRODUCTION

- PERFORMANCE CHARTS 5

- 1

5.3 FLIGHT PLANNING EXAMPLE 5

- 2

5.4 AIRSPEED CALIBRATION 5

- 8

5.5 ALTIMETER CORRECTION 5

- 9

5.6 ALTERNATE STATIC SOURCE 5

- 9

5.7 TEMPER ATURE CORRECTION CHART 5

- 9

5.8 WIND COMPONENT 5

- 9

5.9 STALL SPEED 5

- 12

5.10 TAKE

- OFF DISTANCE 5

- 13

5.11 TWIN ENGINE CLIMB

- MCP CLIMB 5

- 1 5

5.12 ONE ENGINE INOPERATIVE CLIMB 5

- 1 7

5.1 3 BALKED LANDING CLIMB 5

- 19

5.14 TIME, FUEL AND DISTANCE TO CLIMB

- MCP

CLIMB 5

- 21A.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- ii DATE: 23 April 201 5 

### SECTION 5

PERFORMANCE

TABLE OF CONTENTS

P ARAGRAPH P AGE

5.1 5 CRUISE PERFORMANCE

- BEST ECONOMY

MIXTURE

• SEA LEVEL 5

- 2 3

• 3000 FT 5

- 2 4

• 6000 FT 5

- 2 5

• 9000 FT 5

- 26

• 12000 FT 5

- 27

5.1 6 OPERATING ENVELOPE 5

- 28

5.1 7 RANGE PROFILE 5

- 29

5. 18 TIME, FUEL AND DISTANCE TO DESCENT 5

- 3 1

5. 19 LANDING DISTANCE TO CLEAR 50 FT

OBSTACLE 5

- 3 3A.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 1 

### SECTION 5

PERFORMANCE

5.1 GENERAL

This section provides performance information applicable to the P

. 68R,

r equired by certification regulations and u seful for flight planning.

Performance information associated with those optional systems and

equipment which required flight manual supplements are provided by Section

8 (Supplements).



### 5.2 INTRODUCTION

- PERFORMANCE CHARTS

Performance data charts present ed in this Section may be used to know what

to expect from the aircraft under various conditions , and also to facilitate the

planning of flights with reasonable accuracy.

The performance charts are unfactored and do not make any allowance for

varying degre es of pilot proficiency or airframe material or mechanical

deterioration.

NOTE

Performance loss should be expected when

incorporating external modifications causing a

significant increase in the aerodynamic drag.A.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 2 DATE: 23 April 201 5 

### 5.3 FLIGHT PLANNING EXAMPLE

This paragrap h provides information t o facilitate the flight planning by using

the pertinent performance data charts presented in this Section

. The following example illustrates the correct use of the performance charts

.

NOTE

To obtain the fuel quantity in US Gal divid e the

fuel quantity expressed in lbs by 6.01

.

Associated Conditions :

AIRCRAFT

Take

- Off Weight 4200 lbs

Usable fuel 587.3 lbs (97.7 US Gal)

TAKE

- OFF AIRPORT

Outside Air Temperature 2 1 °C (ISA + 10° C )

Pressure altitude 2 000 ft

Wind direction and s peed 180 ° at 8 Kts

Runway direction 330°

CRUISE

Outside Air Temperature ISA

Pressure altitude 6 000 ft

En

- Route Distance 400 n M

ARRIVAL AIRPORT

Outside Air Temperature 2 1 °C (ISA + 10° C )

Pressure altitude 2 000 ft

Wind direction and speed 33 0 ° at 12 Kts

Runway direction 3 0 0°

Procedure:

Take

- Off Distance

The measured take

- off distance s are reported as a function of ambient

temperature, including variations for weight change and wind influence.

1. Calculate the angle between wind direction and runway direction

180°

- 330°=

- 50 °

2. Calculate the wi nd component parallel to runway (from Figure 5

- 3)

5 Kts

- tail windA.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 3 3. Enter Figure 5

- 5 at 21° OAT

4. Proceed horizontally right up to the 2000 ft airport altitude line

5. Proceed vertically downwards to the referen ce line

6. Follow the slope of the adiacent take

- off lines until intersecting the

horizontal 4200 lbs line

7. Proceed vertically downwards to the reference line

8. Follow the slope of the adiacent take

- off lines until intersecting the

horizontal 5 Kts

- tail wind li ne

9. Proceed vertically downwards to obtain the required take

- off distance of

1680 ft (512 m)

Rate of climb

– AEO MCP climb

1. Enter Figure 5

- 6 at 21° OAT

2. Proceed vertically upwards until intersecting the 2000 ft rate

- of

- climb

graph

3. Proceed horizontally right u p to the reference line

4. Follow the slope of the adiacent rate of climb line s until intersecting the

vertical 4200 lbs line

5. Proceed horizontally right to obtain the AEO MCP rate of climb of 1170

ft/min

Rate of climb

– OEI climb

1. Enter Figure 5

- 7 at 2000 ft a irport altitude

2. Proceed horizontally right up to the rate of climb at ISA +10°C

3. Proceed vertically downwards to the reference line

4. Follow the slope of the adiacent rate

- of

- climb lines until intersecting the

horizontal 4200 lbs line

5. Proceed vertically downw ards to obtain the OEI rate of climb of 250

ft/min

Rate of climb

– Balked landing climb

1. Enter Figure 5

- 8 at 2000 ft airport altitude

2. Proceed horizontally right up to the rate of climb at ISA +10°C

3. Proceed vertically downwards the reference line

4. Follow the slope of the adiacent rate

- of

- climb lines until intersecting the

horizontal 4200 lbs line

5. Proceed vertically downwards to obtain the OEI rate of climb of 770

ft/minA.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 4 DATE: 23 April 201 5 Time, Fuel and Distance to Climb

– MCP climb

Time, fuel and distance to climb are determin ed by calculating the difference

between the airport and cruise conditions, thus the indicated procedure must

be followed twice: the first for the airport conditions and the second for the

cruise conditions.

1. Enter Figure 5

- 9 at the given altitude (airport or cruise)

2. Proceed horizontally right up to the time

- to

- climb line at given

temperature

3. Proceed vertically downwards to the reference line

4. Follow the slope of the adiacent time

- to

- climb lines until intersecting the

horizontal 4200 lbs line

5. Proceed vertical ly downwards to obtain the time to climb at the given

altitude

6. Repeat the steps from 1 to 5 to calculate the fuel to climb at the given

altitude

7. Repeat the steps from 1 to 5 to calculate the distance to climb at the given

altitude

In this example the calcu lation gives the following results:

Airport Time to Climb 1.5 min

Cruise Time to Climb 5.2 min

Time to Climb 5.2

- 1.5 = 3. 7 min

Airport Fuel to Climb 4.4 lbs

Cruise Fuel to Climb 13.9 lbs

Fuel to Climb 13.9

- 4.4 = 9.5 lbs (1.6 US Gal)

Airport Dis tance to Climb 3.0 nM

Cruise Distance to Climb 7.0 nM

Distance to Climb 7.0

- 3.0 = 4 .0 nM

Time, Fuel and Distance to Descent

Time, fuel and distance to descent are determined by calculating the

difference between the cruise and landing airport conditio ns, thus the

indicated procedure must be followed twice: the first for the cruise conditions

and the second for the landing airport conditions.

1. Enter Figure 5

- 1 3 at the given altitude (cruise or airport )

2. Proceed vertically up to the time

- to

- descent line re lating to selected R/S

and read the required time to descentA.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 5 3. Proceed vertically up to the fuel

- to

- descent line relating to selected R/S

and read the required fuel to descent

4. Proceed vertically up to the distance

- to

- descent line relating to selected

R/S and read the required distance to descent

In this example the calculation gives the following results , with a selected

R/S of 500 fpm :

Landing Airport Time to Descent 4.0 min

Cruise Fuel to Descent 12 .5 min

Time to Descent 12

. 5

- 4.0 = 8 .5 min

Landing Airport Fuel to Descent 3.5 lbs

Cruise Fuel to Descent 11

. 5 lbs

Fuel to Descent 11

. 5

- 3.5 = 8.0 lbs (1. 3 US Gal)

Landing Airport Distance to Descent 12.1 nM

Cruise Distance to Descent 36.5 nM

Distance to Descent 36.5

- 12.1 = 2 4. 4 nM

Cruise P erformance

– Best Economy Mixture

The cruise distance is obtained by subtracting the calculated distance to climb

and distance to descent from the total en

- route distance :

Cruise Distance = En

- route Distance

- Climb Distance

- Descent Distance

= 400

- 4.0

- 24.4 = 371.6 nM

The cruise power setting should be determined on the basis of the required

and available fuel load.

From the Cruise Performance Table (figure 5

- 1 0 ), at a cruise altitude of 6 000

ft (ISA) and a power rating of 6 5

. 5 % (2350 RPM and 2 2 " Hg), the cruise

airspeed is 159 KTAS at MTOW

. Due to the lower take

- off weight the cruise

airspeed must be increased by 1 Kt

. From the same table, the fuel flow is 18.1 GPH (10 8.8 l bs/hr ) total

. Cruise time and fuel may be calculated by the following formula s :

Cruise Time = Cruise Distance / Cruise Speed

= 371.6 / 16 0 = 2.3 2 hours or 13 9

. 3 min

Cruise Fuel = Fuel Flow x Cruise Time

= 18.1 x 2.3 2 = 4 2

. 0 US Gal (25 2

. 4 lbs)A.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 6 DATE: 23 April 201 5 Total Flight Time

The total flight time is determined by adding time to climb, cruise time, and

time to descen t :

Total Flight Time = Time to Climb + Cruise Time + Time to Descent

= 3.7 + 13 9

. 3 + 8.5 = 15 1

. 5 min

Total Required Fuel

The total required fuel is obtained by adding fuel for start, taxi and take

- off

(20 lbs) , fuel to climb, cruise fuel , and fuel to descen t :

Total Required Fuel = Fuel for Start, Taxi and Take

- Off + Fuel to Climb +

Cruise Fuel + Fuel to Descent

= 20.0 + 9.5 + 25 2

. 4 + 8.0 = 28 9

. 9 lbs ( 48

. 2 US Gal)

Reserve Fuel

The reserve fuel is determined by subtracting the calculated t otal required

fuel from the usable fuel:

Reserve Fuel = Usable Fuel

- Total Required Fuel

= 587.3

– 28 9

. 9 = 29 7

. 4 lbs (49. 5 US Gal)

Reserve fuel must exceed 60 lbs to allow a minimum of 45 min utes of flight

time at 45% power (2200 RPM)

.

Landing Distance

Th e measured landing distance s (ove r 50 ft obstacle) are reported as a

function of ambient temperature, including variations for weight change and

wind influence.

1. Calculate the landing weight by substracting the total required fuel from

the take

- off weight

= 4200

- 28 9

. 9 = 3910

. 1 lbs

2. Calculate the angle between wind direction and runway direction

330°

- 300°= 30 °

3. Calculate the wi nd component parallel to runway (from Figure 5

- 3)

10 Kts

- head wind

4. Enter Figure 5

- 1 4 at 21° OAT

5. Proceed horizontally right up to t he 2000 ft landing airport altitude line

6. Proceed vertically downwards to the reference line

7. Follow the slope of the adiacent landing distance lines until intersecting

the horizontal 391 0 lbs lineA.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 7 8. Proceed vertically downwards to the reference line

9. Follow th e slope of the adiacent take

- off lines until intersecting the

horizontal 10 Kts

- headwind line

10. Proceed vertically downwards to obtain the required landing distance of

1 36 0 ft ( 414 m)A.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 8 DATE: 23 April 201 5 

### 5.4 AIRSPEED CALIBRATION

a. Airspeed Indicator System Error vs. I.A .S.

b. Airspeed Indicator System Error vs. C.A.S.

Figure 5

- 1

AIRSPEED CALIBRATIONA.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 9 

### 5.5 ALTIMETER C ORRECTION

The maximum static error correction to be applied to the altimeter reading

does not exceed 30 feet.



### 5.6 ALTERNATE STATIC SOURCE

The alte rnate source valve is located on the left side of the control pedestal.

No static error correction must be applied to the altitude and airspeed

indicator readings when static air is supplied by the alternate static source.



### 5.7 TEMPERATURE CORRECTION CHART

See Figure 5

- 2.



### 5.8 WIND COMPONENT

See Figure 5

- 3.

Maximum demonstrated crosswind velocity for take

- off and landing is 25

K t s.A.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 10 DATE: 23 April 201 5 Figure 5

- 2

TEMPERATURE CONVERSIONA.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 11 Figure 5

- 3

WIND COMPONENTA.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 12 DATE: 23 April 201 5 

### 5.9 STALL SPEED

(Figure 5

- 4)

Associated Conditions :

Th rottles IDLE

NOTE

Maximum altitude loss experienced during

conventional stall is 120 feet.

Maximum altitude loss experienced during one

engine inoperative stall is 500 feet.

CONFIGURATION ANGLE OF BANK

0° 30° 60°

Weight

(kg) FLAPS GEAR KIAS KIAS KIAS

2063 0° UP 67 72 95

0° DOWN 67 72 95

15° UP 64 69 91

15° DOWN 64 69 91

35° DOWN 61 65 86

1960 0° UP 65 70 93

0° DOWN 65 70 93

15° UP 62 67 89

15° DOWN 62 67 89

35° DOWN 60 64 84

Figure 5

- 4

STALL SPEEDA.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 13 

### 5.10 TAKE

- OFF DISTANCE

(Figure 5

- 5)

Associated Conditions :

Power 2700 RPM, full throttle, before brake release

Flaps 15°

Level, Hard Surface, Dry Runway

WARNING

Poor maintenance condition of the airplane,

deviation from the given procedures as well as

unfavorable external factors ( e.g. high

temperature, rain, unfavorable wind

conditions, including cross

- wind) will increase

the take

- off distance.

CAUTION

 The Ground Run is approx. 60% of T ake

- O ff

Distance.

 Increase Ground Run by 2 5% when operating

from a grass surface

. These values ar e typical ones . On wet ground or

wet soft grass covered runways, the Ground Run

may beco me significantly longer than stated

above

.A.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 14 DATE: 23 April 201 5 Figure 5

- 5

TAKE

- OFF DISTANCEA.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 15 

### 5.1 1 TWIN ENGINE CLIMB

- MCP CLIMB

(Figure 5

- 6 )

Associated Conditions :

Power 270 0 RPM, full throttle

Mixture FULL RICH up to 5000 ft ; at higher

altitude LEAN for smooth operations

. Do not exceed 435°F (224°C) CHT

Flaps UP

Landing Gear UP

Best Rate

- of

- Climb Speed 88 KIASA.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 16 DATE: 23 April 201 5 Figure 5

- 6

TWIN ENGINE CLIMB

- M CP CLIMBA.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 17 

### 5.1 2 ONE ENGINE INOPERATIVE CLIMB

(Figure 5

- 7 )

Associated Conditions :

Power 2700 RPM, full throttle

Mixture FULL RICH up to 5000 ft ; at higher

altitude LEAN for smooth operations

. Do not exceed 435°F (224°C) CHT

Flaps UP

Landing Gear UP

Best Rate

- of

- Climb Speed 88 KIASA.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 18 DATE: 23 April 201 5 0 1000 2000 3000 4000 5000 6000 7000 8000 9000 10000 11000

-100 0 100 200 300 400 500ALTITUDE [ft]

ISA

ISA+10°C

ISA+20°C

ISA+30°C

3500 3700 3900 4100 4300 4500 4700

-100 0 100 200 300 400 500

RATE OF CLIMB [fpm]WEIGHT [lbs] REFERENCE LINE

Figure 5

- 7

ONE ENGINE INOPERATIVE CLIMBA.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 19 

### 5.1 3 BALKED LANDING CLIMB

(Figure 5

- 8 )

Associated Conditions :

Power 2700 RPM, full throttle

Mixture FULL RICH up to 5000 ft ; at higher

altitude LEAN for smooth operations

. Do not exceed 435°F (224°C) CHT

Flaps 35°

Landing Gear DOWN

Balked Landing Transition Speed 80 KIASA.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 20 DATE: 23 April 201 5 0 100 200 300 400 500 600 700 800 900 1000 1100 1200ALTITUDE [ft] ISA

ISA+10°C

ISA+20°C

ISA+30°C

0 100 200 300 400 500 600 700 800 900 1000 1100 1200

RATE OF CLIMB [fpm]WEIGHT [lbs] REFERENCE LINE 0 2,000 4,000 8,000 10,000

4,500

4,300

3,90 0

3,700

3,500

Figure 5

- 8

BALKED LANDING CLIMBA.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 21 

### 5.1 4 TIME

, FUEL AND DISTANCE TO CLIMB

- M CP

CLIMB

(Figure 5

- 9 )

Associated Conditions :

Power 2700 RPM, full throttle

Mixture FULL RICH up to 5000 ft ; at higher

altitude LEAN for smooth operations

. Do not exceed 435°F (224°C) CHT

Flaps UP

Landing Gear UP

Best Rate

- of

- Climb Speed 88 KIA S

NOTE

To obtain the total fuel used, add 20 lbs for start,

taxi and take

- off.A.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 22 DATE: 23 April 201 5 Figure 5

- 9

TIME

, FUEL AND DISTANCE TO CLIMB

- MCP CLIMBA.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 23 

### 5. 1 5 CRUISE PERFORMANCE

- BEST ECONOMY

MIXTURE

 SEA LEVEL

NOTES

1. Increase speed by 1 KTAS for each 200 lbs

below 4548 lbs

2. To obtain the fuel flow in lbs/h multiply the

fuel flow in GPH by 6.01

ALTITUDE POWER

SETTING I. S. A.

- 20 °C I. S. A. I. S. A. +20 °C

RPM "Hg %BHP KTAS GPH %BHP KTAS GPH %BHP KTAS GPHSEA LEVEL 2450 25 77. 7 160 21 .1 75.0 161 20.5 72.5 162 20.0

2450 23 69. 8 153 19.5 67.3 154 18.8 65.1 155 18.5

2450 21 61.2 146 17.5 59.0 146 17.1 57.1 147 16.6

2450 19 5 3

. 3 138 15.8 51.4 138 15.5 49.7 139 15.1

2 40

0 25 76.2 158 20.6 73.5 160 20.0 71.7 161 19.5

24

0 0 23 6 7

. 9 152 18.8 65.5 153 18.3 63.3 154 17.8

240 0 21 6 0

. 4 145 17.1 58.3 146 16.8 56.4 146 16.3

240 0 19 5 2

. 1 136 15.5 50.3 137 15.0 48.6 137 14.6

2350 25 74.1 157 20.0 71.5 158 19.5 69.1 159 19.0

2350 23 66.3 150 18.3 64.0 151 17.8 6 1.9 152 17.3

2350 21 58.6 143 16.6 56.5 144 16.1 54.6 144 15.8

2350 19 50. 8 135 15.0 49 135 14.6 47.4 136 14.3

2 3 00 25 72.6 155 19.5 70.0 156 19.0 67.7 157 111

2 3 00 23 64.8 149 17.8 62.5 150 17.3 60.4 150 16.8

2 3 00 21 57.0 141 16.1 5 5.0 142 15.6 53.2 143 15.3

2 3 00 19 49.8 135 14.6 48.0 135 14.1 46.4 136 13.8

Figure 5

- 1 0

Sheet 1 of 5A.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 24 DATE: 23 April 201 5 

###  3 000 ft

NOTES

1. Increase speed by 1 KTAS for each 200 lbs

below 4548 lbs

2. To obtain the fuel flow in lbs/h multiply the

fuel flow in GPH by 6.0 1

ALTITUDE POWER

SETTING I. S. A.

- 20 °C I. S. A. I. S. A. +20 °C

RPM "Hg %BHP KTAS GPH %BHP KTAS GPH %BHP KTAS GPH3000 feet 2450 25 81.3 166 22.0 78.4 167 21.3 75.8 168 20.6

2450 23 73.0 159 20.1 70.4 160 19.5 68.0 161 19.0

2450 21 64.5 152 18.3 62.2 152 17.8 60.1 153 17.3

2450 19 56.2 144 16.5 54.2 144 16.0 52.4 144 15.6

2400 24 75.2 161 20.5 72.5 162 19.8 70.1 163 19.3

2400 22 67.2 154 18.6 64.8 155 18.1 62.6 155 17.6

2400 20 58.6 146 16.8 56.5 146 16.3 54.6 1 47 16.0

2400 18 50.8 136 15.1 49.0 137 14.8 47.4 137 14.5

2350 24 73.1 159 19.8 70.5 160 19.3 68.1 161 18.6

2350 22 65.4 152 18.1 63.0 153 17.6 60.9 154 17.1

2350 20 57.3 145 16.3 55.2 145 16.0 53.4 145 15.5

2350 18 49.5 135 14 .6 47.8 135 14.3 46.1 135 14.0

2300 24 71.6 158 19.3 69.0 159 18.8 66.7 159 18.3

2300 22 63.8 151 17.6 61.5 151 17.1 59.4 152 16.6

2300 20 56.0 143 16.0 54.0 143 15.5 52.2 144 15.1

2300 18 48.1 133 14.1 46.4 133 13.8 44.8 133 13. 5

Figure 5

- 1 0

Sheet 2 of 5A.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 25 

###  6 000 ft

NOTES

1. Increase speed by 1 KTAS for each 200 lbs

below 4548 lbs

2. To obtain the fuel flow in lbs/h multiply the

fuel flow in GPH by 6.0 1

ALTITUDE POWER

SETTING I. S. A.

- 20 °C I. S. A. I. S. A. + 20 °C

RPM "H g %BHP KTAS GPH %BHP KTAS GPH %BHP KTAS GPH6000 feet 2450 24 79.9 170 21.6 77.0 170 21.0 74.4 171 20.5

2450 22 72.2 163 20.0 69.5 164 19.3 67.1 164 18.8

2450 20 63.3 155 18.0 61.0 155 17.5 58.9 155 17.0

2450 18 54.5 144 16.1 52.5 144 15.6 50 .7 144 15.3

2400 24 78.4 168 21.1 75.5 169 20.5 72.9 169 20.0

2400 22 70.1 161 19.3 67.5 162 18.8 65.2 162 18.3

2400 20 61.3 154 17.5 59.0 154 17.0 57.0 154 16.5

2400 18 53.4 143 15.6 51.4 143 15.3 49.6 143 14.8

2350 24 75.8 166 20.3 73.0 166 19.8 70.5 167 19.3

2350 22 68.0 159 18.6 65.5 159 18.1 63.3 160 17.6

2350 20 59.7 151 17.0 57.5 151 16.5 55.5 151 16.0

2350 18 52.2 142 15.3 50.3 141 14.8 48.6 141 14.5

2300 24 74.1 165 19.8 71.4 165 19.3 6 8.9 165 18.6

2300 22 66.4 158 18.1 64.0 158 17.6 61.8 158 17.1

2300 20 58.5 149 16.5 56.3 149 16.0 54.4 149 15.6

2300 18 50.5 139 14.8 48.6 139 14.3 46.9 139 14.0

Figure 5

- 1 0

Sheet 3 of 5A.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 26 DATE: 23 April 201 5 

###  9 000 ft

NOTES

1. Increase speed by 1 KTAS for each 200 lbs

below 4548 lbs

2. To obtain the fuel flow in lbs/h multiply the

fuel flow in GPH by 6.0 1

ALTITUDE POWER

SETTING I. S. A.

- 20 °C I. S. A. I. S. A. + 20 °C

RPM "Hg %BHP KTAS GPH %BHP KTAS GPH %BHP KTAS GPH9000feet 2450 21 70.2 171 19.5 67.6 172 19.0 65.2 171 18.5

2450 20 66.0 162 18.6 63.5 162 18.0 61.3 162 17.6

2450 19 61.5 157 17.6 59.2 157 17.1 57.1 157 16.6

2450 18 57.2 153 16.6 55.0 152 16.1 53.1 152 15.8

2400 21 68.4 164 19.0 65.8 165 18.3 63.5 164 17.8

2400 20 63.9 159 18.0 61.5 160 17.5 59.3 159 17.0

2400 19 59.8 155 17.1 57.5 155 16.6 55.5 155 16.1

2400 18 55.6 151 16.1 53.5 150 15.6 51.6 150 15.3

2350 21 66.5 162 18.3 64.0 162 17.8 61.8 162 17.3

2350 20 62.2 158 17.5 59.9 158 17 .0 57.8 157 16.5

2350 19 58.1 153 16.5 55.9 153 16.1 53.9 152 15.6

2350 18 54.5 148 15.8 52.4 148 15.3 50.6 148 15.0

2300 21 64.9 161 17.8 62.5 160 17.3 60.3 160 16.8

2300 20 60.6 156 17.0 58.3 156 16.5 56.3 155 16.0

2300 19 56 .6 152 16.0 54.5 151 15.6 52.6 151 15.1

2300 18 52.6 146 15.1 50.6 145 14.8 48.8 145 14.3

Figure 5

- 1 0

Sheet 4 of 5A.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 27 

###  1 2 000 ft

NOTES

1. Increase speed by 1 KTAS for each 200 lbs

below 4548 lbs

2. To obtain the fuel flow in lbs/h multiply the fuel

f

low in GPH by 6.0 1

ALTITUDE POWER

SETTING I. S. A.

- 20 °C I. S. A. I. S. A. +20 °C

RPM "Hg %BHP KTAS GPH %BHP KTAS GPH %BHP KTAS GPH12000 feet 2450 19 64.0 165 18.1 61.5 165 17.6 59.3 163 17.1

2450 18 59.6 160 17.1 57.3 160 16.6 55.2 160 16.3

2450 17 55.1 153 16.3 53.0 153 15.8 51.1 155 15.3

2400 19 62.4 163 17.6 60.0 163 17.1 57.9 163 16.6

2400 18 58.0 158 16.6 55.8 158 16.1 53.8 158 15.8

2400 17 53.8 157 15.8 51.7 152 15.3 49.8 152 15.0

2400 16 49.4 146 14.8 47.5 146 14.3 45.8 146 14.0

2350 19 60.3 160 17.0 58.0 160 16.5 55.9 161 16.1

2350 18 56.4 156 16.1 54.2 156 15.6 52.3 156 15.3

2350 17 52.4 150 15.3 50.4 150 14.8 48.6 150 14.5

2350 16 48.3 144 14.3 64.4 144 14.0 44.7 144 13.6

2300 19 58.8 158 16.5 56.5 158 16.0 54.5 159 15.6

2300 18 54.6 152 15.6 52.5 152 15.1 50.6 153 14.8

2300 17 50.5 148 14.8 48.6 147 14.3 46.9 147 14.0

2300 16 46.5 141 13.8 44.8 141 13.5 43.2 141 13.1

Figure 5

- 1 0

Sheet 5 o f 5A.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 28 DATE: 23 April 201 5 

### 5. 1 6 OPERATING ENVELOPE

(Figure 5

- 1 1 )

Associated Conditions :

Aircraft Weight 4 548 lbs

Outside Air Temperature ISA

Wind ZERO

Flaps UP

Landing Gear UP

0 4000 8000 12000 16000 20000 24000

50 60 70 80 90 100 110 120 130 140 150 160 170 180 190 200

TRUE AIR SPEED [kts]ALTITUDE [ft] 2700 rpm

FULL THROTTLE

75% @ 2450 rpm 65% @ 2450 rpm 55% @ 2350 rpm STALL SPEED

Figure 5

- 1 1

CRUISE SPEED vs . ALTITUDEA.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 29 

### 5. 1 7 RANGE PROFILE

(Figure 5

- 1 2 )

Associa ted Conditions :

STD RANGE CONFIGURATION

Aircraft Weight 4 548 lbs

Total Fuel 520 lt

Climb to desired altitude

Mixture BEST ECONOMY

Ambient ISA, zero wind

Rate of descent 750 fpm

LONG RANGE CONFIGURATION

Aircraft Weight 4 548 lbs

Total Fue l 670 lt

Climb to desired altitude

Mixture BEST ECONOMY

Ambient ISA, zero wind

Rate of descent 750 fpm

NOTE

Range computation includes 20 lbs of fuel for

start, taxi and take

- off, plus the fuel required

climb, cruise and descent , plus 45min reserve

fuel a t 45% power.A.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 30 DATE: 23 April 201 5 Figure 5

- 1 2

RANGE PROFILEA.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 31 

### 5. 18 TIME, FUEL AND DISTANCE TO DESCENT

(Figure 5

- 1 3 )

Associated Conditions :

Power As required

Mixture BEST ECONOMY

Flaps UP

Landing Gear UP

Airspeed 158 KIAS

NOTE

Distances shown are for zero wind. Th ese

information may be used for all descent weights.A.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 32 DATE: 23 April 201 5 Figure 5

- 1 3

TIME, FUEL AND DISTANCE TO DESCENTA.F.M. P/N NOR10.707

- 30 C

Section 5

P

. 68R PERFORMANCE

Rev. 27

DATE: 23 April 201 5 5

- 33 

### 5. 19 LANDING DISTANCE TO CLEAR 50 FT

OBSTACLE

(Figure 5

- 1 4 )

Associated Conditions :

Throttle IDLE at 50 ft above ground level

Flaps 35°

Maximum effective braking

Level, Hard Surface, Dry Runway

Speed at 50 ft obstacle 1.3 V s0

CAUTION

Increase Ground Run by 12 % when operating

from a grass surface

.A.F.M. P/N NOR10.707

- 30 C

Section 5

PERFORMANCE P

. 68R

Rev. 27

5

- 34 DATE: 23 April 201 5 Figure 5

- 1 4

LANDING DISTANCE